Landing assist apparatus eccentric bushing

ABSTRACT

An aircraft landing assist apparatus is designed to be retrofit to existing aircraft having internal constructions that have been modified to support the apparatus. The apparatus is designed so that on rough landings of the aircraft on a ship deck, the apparatus will collapse in a controlled manner to avoid any damage to ammunition and/or fuel storage areas of the aircraft.

This invention was developed in the course of work under U.S. GovernmentArmy Contract DMH23-99-C-0111. The U.S. government may possess certainrights in the invention.

BACKGROUND OF THE INVENTION

(1) Field of the Invention

The present invention pertains to an aircraft landing assist system.More specifically, the present invention pertains to a mounting systemfor an aircraft landing assist probe, and a method of retrofitting anaircraft with the mounting system to adapt that aircraft for landing ona deck of a ship.

(2) Description of the Related Art

Landing assist systems have been developed that facilitate the landingof an aircraft, for example, a helicopter, on the deck of a ship. Anexample of one such system is the aircraft/ship integrated secure andtraverse (ASIST) deck landing system developed by Indal Technologies,Inc. of Ontario, Canada.

In a typical aircraft landing assist apparatus employed in landing ahelicopter on the deck of a ship, the helicopter is provided with alanding probe. The landing probe is positioned on an underside of anaircraft and projects downwardly from the aircraft to a distal end ofthe probe.

A rapid securing device is provided on the deck of the ship. The rapidsecuring device includes a track on the ship deck and a cart mounted onthe track for sliding movement of the cart along the track. The cart isprovided with a securing latch that is removably attachable to the probedistal end.

In landing a helicopter on the deck of a ship using the aircraft landingassist system, the helicopter approaches the ship deck when the pitchingmotion of the ship is relatively tranquil. As the helicopter descendstoward the ship deck, the cart moves along the track, following themovement of the helicopter over the ship deck toward a predeterminedlanding area. On touchdown of the helicopter landing gear on the decklanding area, the landing probe of the helicopter is received andsecured by the latch of the cart, securing the helicopter to the shipdeck. With the helicopter secured to the ship deck, the cart can then bemoved across the deck to move the helicopter to a hangar.

Helicopters that are designed for ship deck landings are equipped withlanding assist probes. When this type of helicopter is constructed, thestructural frame of the helicopter is matched to the landing assistprobe to provide sufficient structural strength to the probe. Thismatching of the structural frame of the helicopter with the landingassist probe is necessary because on a pitching and rolling ship deck,there is a great deal of tension on the probe as it holds the helicopterdown on the deck. Helicopters by design are top heavy with the rotorassembly and the power unit being positioned in the upper area of thehelicopter's structural frame. Thus, known aircraft/ship landing assistsystems employ helicopters that have structural frames specificallydesigned for the landing assist probe that secures the helicopter to theship deck.

The prior art aircraft/ship landing assist systems are thereforedisadvantaged in that the systems are limited to use with helicoptersthat are dedicated for use with the landing assist system. In theconstruction of these dedicated helicopters, a primary designconsideration is providing the helicopter with a structural frame thatis secured to the landing assist probe to facilitate shipboard landingsof the helicopter. These specifically designed helicopters may belacking in other desirable features for helicopters, for example thevarious different types of weaponry available on modern day militaryaircraft. What is needed to overcome this disadvantage of aircraft/shiplanding assist systems is an aircraft landing assist apparatus that canbe retrofit to existing aircraft to adapt these aircraft for shipboardoperation.

SUMMARY OF THE INVENTION

The present invention overcomes disadvantages of the prior art byproviding an aircraft landing assist apparatus that is specificallydesigned to be retrofit to existing aircraft that have not previouslybeen designed for shipboard landings. In addition, on rough landing ofan aircraft using the apparatus, the apparatus is designed to collapsein a controlled manner beneath the aircraft, thereby avoiding any damageto ammunition and/or fuel storage areas of the aircraft, and preventingthe transfer of the vertical loads due to impact to the pilot and/orcopilot.

The apparatus basically comprises a landing probe assembly that issecured to the underside of an aircraft, preferably a helicopter. Priorto the installation of the landing probe assembly, the internalstructure of the helicopter is modified to provide sufficient structuralstrength to the helicopter for landing the helicopter on the deck of aship and securing the helicopter to the deck of the ship through thelanding probe.

In the method of modifying the aircraft, a fuselage panel on theunderside of the aircraft is first removed, exposing an interior bay ofthe aircraft. The interior bay has a forward bulkhead wall and arearward bulkhead wall at opposite ends of the bay. In militaryhelicopter aircraft the bay houses an ammunition container. Removal ofthe fuselage bottom panel exposes the ammunition container in the bay.The ammunition container is removed, providing access to the forward andrearward bulkhead walls in the bay.

To provide sufficient structural strength to the aircraft structure tofacilitate use of the aircraft landing assist apparatus, both theforward bulkhead wall and rearward bulkhead walls are removed andreplaced by reinforced bulkhead walls. The reinforced bulkhead wallsprovide sufficient structural strength to the helicopter frame tosupport the rotor assembly and power unit of the aircraft, as well assupport the landing assist apparatus of the invention.

With the reinforced forward and rearward bulkhead walls installed in theaircraft at opposite sides of the interior bay, the ammunition containeris reinstalled in the bay. The bottom fuselage panel is then reinstalledon the underside of the aircraft, enclosing the ammunition containerinside the bay.

The aircraft landing assist apparatus of the invention is basicallycomprised of a landing probe that is suspended from an underside of thehelicopter by a base that is connected to the helicopter. A plurality ofstabilizing struts extend between the probe and the base. The strutshold the probe in a position where the probe extends downwardly andslightly forwardly from a central portion of the base.

The base of the landing assist apparatus is connected to the undersideof the aircraft. The base has a general X-shaped configuration, with abase central portion and four radiating arms. Distal ends of two of thearms are secured to the forward reinforced bulkhead and distal ends ofthe remaining two arms are secured to the rearward reinforced bulkhead.Thus, the apparatus is basically supported from the same internalconstruction of the aircraft that receives the loads when the aircraftis flying.

The landing probe of the apparatus is a telescoping probe havingopposite proximal and distal ends. The distal end of the probe retractsrelative to the proximal end of the probe when a compressive force isexerted on the probe distal end.

The probe proximal end is connected to the central portion of the basefor movement of the probe relative to the base. In the preferredembodiment, the probe proximal end is provided with a connector havingperpendicular pivot shafts that enable pivoting movement of the probe intwo perpendicular planes about two perpendicular axes. One of the pivotshaft ends is provided with a journal having a smaller cross sectiondiameter than the remaining three journals of the pivot shafts. Shouldan excessive compressive force due to a rough landing be exerted againstthe probe distal end causing complete retraction of the probe distal endrelative to the proximal end and exerting a compressive force on theprobe proximal end, the small diameter journal will first fail, causingthe probe to collapse beneath the base preventing the probe from beingpushed upwardly through the center of the helicopter fuselage bottompanel and into the ammunition container in the helicopter bay.

The four stabilizing struts extending between the base and the probehold the probe in its downwardly extending position. The struts resistmovement of the probe when a compressive force on the probe exerts atensile force on the struts. The struts are specifically designed tocollapse when a compressive force is exerted on the struts, therebyproviding no resistance of movement of the probe that exerts acompressive force on the struts. In this manner, the movement of theprobe is controlled when an excessive impact force is exerted on theprobe due to a hard landing of the helicopter on the ship deck. Thecontrolled movement of the probe prevents the probe proximal end frompiercing the bottom fuselage panel of the helicopter and potentiallyentering into the ammunition container or a fuel cell.

Different embodiments of the stabilizing struts are employed on thelanding assist apparatus. In one embodiment, each strut is comprised ofa plurality of links connected end to end by pivot connectors. Thelengths of each strut limit movement of the probe when the probemovement exerts a tensile force on the strut, but each strut is designedto collapse and permit movement of the probe when the probe movementexerts a compressive force on the strut.

Some of the strut links include pivot connections having an eccentricbushing. The eccentric bushing can be rotated relative to the strut linkto adjust the overall length of the strut.

In a further embodiment of the stabilizing struts, each strut includesbands constructed of composite materials. The bands are looped aroundproximal and distal end connectors at the opposite proximal and distalends of the strut. The proximal end connector connects the strut to theapparatus base, and the distal end connector connects the strut to theprobe. The composite material of the strut bands resist movement of theprobe when the probe movement exerts a tensile force on the bands, butbends and permits movement of the probe when the probe movement exerts acompressive force on the bands.

The distal ends of the stabilizing struts are operatively connected tothe probe by a slip ring. The slip ring is mounted on the probe formovement of the slip ring along the probe length in response to apredetermined amount of movement of the probe distal end relative to theprobe proximal end. This enables the slip ring to move relative to theprobe in response to a significant impact of the probe distal end with aship deck on a rough landing of the helicopter. The movement of the slipring controls the collapse of the stabilizer struts and the movement ofthe probe in response to the impact.

The slip ring is provided with a lock mechanism that holds the slip ringstationary relative to the probe with the probe proximal and distal endsin their extended positions. On impact of the probe distal end with theship deck, the slip ring continues to hold the stabilizer strut distalends stationary relative to the probe for a predetermined movement ofthe probe distal end relative to the probe proximal end. The tension onthe struts maintains the position of the probe relative to thehelicopter. When movement of the probe distal end relative to the probeproximal end exceeds the predetermined amount of movement, the lockmechanism of the ring is released and the ring, as well as the attachedstabilizer strut distal ends, are free to move along the length of theprobe to control the collapse of the probe beneath the helicopter.

The aircraft landing assist apparatus of the invention described aboveenables existing helicopters to be retrofit with the apparatus, adaptingthe helicopters for shipboard landings. The apparatus is alsoconstructed whereby it will controllably collapse in response to anexcessive impact of the apparatus with a ship deck on rough landing ofthe helicopter, thereby avoiding potentially catastrophic damage to thehelicopter.

BRIEF DESCRIPTION OF THE DRAWINGS

Further features of the present invention are set forth in the followingdetailed description of the preferred embodiment of the invention, andin the drawing figures wherein:

FIG. 1 is a view of one example of a helicopter aircraft retrofit withthe landing assist apparatus of the invention;

FIG. 2 is a side elevation view of the landing assist apparatus removedfrom the aircraft;

FIG. 3 is a front elevation view of the apparatus;

FIG. 4 is a top perspective view of the apparatus employing a firstembodiment of stabilizing struts;

FIG. 5 is a partial view of the apparatus base;

FIG. 6 is a partial view of the apparatus probe shown removed from theapparatus base;

FIG. 7 is a partial view of an end of a strut link shown in FIG. 4;

FIG. 8 is a view of an eccentric bushing removed from the strut link ofFIG. 7;

FIG. 9 is a bottom perspective view of the apparatus employing a secondembodiment of stabilizing struts;

FIG. 10 is a view of a stabilizing strut removed from the apparatus ofFIG. 9;

FIG. 11 is a partial view of an end connector of the stabilizing strutof FIG. 10;

FIG. 12 is a view of the end connector removed from the stabilizingstrut;

FIG. 13 is a partial, sectioned view of the landing probe and lockmechanism of the apparatus;

FIG. 14 is a view of the underside of the aircraft, with the bottomfuselage panel being removed;

FIG. 15 is a view of the underside of the aircraft, with the ammunitioncontainer being removed;

FIG. 16 is a view into the aircraft bay, showing removal of an existingforward bulkhead;

FIG. 17 is a view into the forward end of the aircraft bay showinginsertion of a modified, reinforced forward bulkhead;

FIG. 18 is a view into the forward end of the aircraft bay showing thereinforced forward bulkhead installed;

FIG. 19 is a view into the rearward end of the aircraft bay showing theexisting rearward bulkhead;

FIG. 20 is a view into the rearward end of the bay showing theinstallation of a reinforcement of the rearward bulkhead;

FIG. 21 is a view into the rearward end of the bay showing thereinforced bulkhead installed;

FIG. 22 is a view of the underside of the aircraft showing the apparatusinstalled;

FIG. 23 is a side view of an initial stage of operation of the landingassist apparatus;

FIG. 24 is a side view of the operation of the apparatus, subsequent tothat of FIG. 23;

FIG. 25 is a side view of the operation of the apparatus, subsequent tothat of FIG. 24;

FIG. 26 is a side view of the operation of the apparatus, subsequent tothat of FIG. 25;

FIG. 27 is a side view of the operation of the apparatus, subsequent tothat of FIG. 26; and

FIG. 28 is a side view of the operation of the apparatus similar to thatof FIG. 27, but showing the operation of the alternate stabilizingstruts.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

FIG. 1 shows the aircraft landing assist apparatus 12 of the inventionemployed on an aircraft 14. Specifically, FIG. 1 shows the apparatus 12installed on the underside of a helicopter-type aircraft, for example anAH64 Apache helicopter. It should be understood that the particular typeof aircraft 14 with which the apparatus 12 is shown in FIG. 1 isillustrative only. It is not intended that the apparatus 12 be limitedto use with any one particular type of aircraft.

The apparatus 12 is specifically designed to be retrofit to existinghelicopters that have not previously been designed for shipboardlandings. In addition, on rough landing of the aircraft using theapparatus 12, the apparatus is designed to collapse in a controlledmanner beneath the aircraft 14, thereby avoiding any damage to internalcomponents of the aircraft such as an ammunition container and/or a fuelstorage cell. Although the preferred embodiment of the apparatus isretrofit to an existing aircraft, the apparatus may also be made anintegral part of the aircraft as the aircraft is initially assembled.

Prior to the installation of the landing assist apparatus 12 on theunderside of the aircraft 14, the internal structure of the aircraft ismodified. The modifications provide sufficient structural strength tothe aircraft for landing the aircraft on the deck of a ship and forlatching the aircraft to the ship deck using a conventional deck landingsystem such as the aircraft/ship integrated secure and traverse (ASIST)system produced by Indal Technologies, Inc. of Ontario, Canada. Themethod of modifying the structure of the aircraft in order to retrofitthe landing assist apparatus is also a part of the present invention.

FIGS. 2 and 3 show the construction of the aircraft landing assistapparatus 12 removed from the underside of the aircraft 14 shown inFIG. 1. The apparatus 12 is basically comprised of a landing probe 16that is suspended from a base 18 that is connected to the underside ofthe aircraft. A plurality of stabilizing struts 22 extends between theprobe and the base. The struts 22 restrain movement of the probe 16 andhold the probe in a position extending downwardly and slightly forwardlyfrom the aircraft.

Apparatus Base

FIGS. 2-5 show the construction of the base 18 of the apparatus. Thebase 18, as well as the other structural parts of the apparatus, areconstructed of metals or composite materials typically used in theconstruction of aircraft. As best seen in FIGS. 4 and 5, the base has ageneral X-shape with a central portion 24 and four arms that radiateoutwardly from the central portion. Each of the arms 26, 32 is formedwith a U-shaped cross section, which provides structural strength to thearms, yet will crush to absorb excessive impact loads. Two of the arms26 extend forwardly from the base central portion 24 to distal ends 28of the forward arms. Two of the arms 32 extend rearwardly from the basecentral portion 24 to distal ends 34 of the rearward arms. As best seenin FIG. 4, the arm distal ends 28, 34 are spatially arranged around thebase central portion 24 and are positioned in a polygonally patternaround the base central portion. Each of the arm distal ends 28, 34 areadapted for connection to the underside of the aircraft 14.

The underside of the base central portion 24 is shown in FIG. 5. Aforward bearing assembly 36 and a rearward bearing assembly 38 aresecured to the base central portion 24 by a pair of clamps 42. Theforward bearing assembly 36 and the rearward bearing assembly 38 have acommon center axis 44, that is aligned with a center axis (not shown) ofthe aircraft 14. The forward bearing assembly 36 has a slightly smallerinterior diameter than the rearward bearing assembly 38. Thus, theforward bearing assembly 36 receives a smaller journal than the rearwardbearing assembly 38, as will be explained.

A pair of semicylindric recesses 46 are formed into the base centralportion 24. The recesses 46 have a common center axis (not shown) thatis perpendicular to the bearing assembly center axis 44. The recesses 46provide clearance in the base central position for movement of the probe16 beneath the base 18, as will be explained.

Apparatus Probe

FIGS. 2-4 show the landing assist probe 16 depending from the base 18,and FIG. 6 shows the landing probe 16 removed from the base. The probe16 has a cylindrical length that extends between opposite proximal 52and distal 54 ends of the probe. The cylindrical configuration of theprobe 16 has a center axis 56 that defines mutually perpendicular axialand radial directions relative to the probe. The construction of theprobe 16, for the most part, is the same as that of conventional probesemployed in landing assist systems such as the ASIST system. The probedistal end 54 is adapted for being latched by a latching mechanism of alanding assist system. The probe proximal end 52 is adapted forconnection to the underside of an aircraft. A distal portion 58 of theprobe is telescopically received in a proximal portion 62 of the probe.This enables telescoping, reciprocating movement of the probe distalportion 58 into the probe proximal portion 62 in response to acompressive force being exerted on the probe distal end 54 duringlanding operations.

A spring assembly or shock absorbing assembly (not shown) is containedinside the interior of the probe 16 and biases the probe distal endportion 58 toward an extended position relative to the probe proximalportion 62, as is conventional. The spring assembly or shock absorberassembly contained in the probe 16 resists or is biased against themovement of the probe distal end portion 58 toward the probe proximalend portion 62 in response to an impact or compressive force beingexerted on the probe distal end 54.

A probe connector assembly 64 connects the probe proximal end 52 to thebase central portion 24 for movement of the probe 16 relative to thebase 18. As shown in FIG. 6, the connector assembly 64 includes a pairof flanges 66 that are secured stationary to opposite sides of the probeproximal end 52. The flanges 66 project both axially and radially fromthe probe proximal end and are oriented at an angle relative to theprobe center axis 56. Each of the flanges 66 has a shaft hole 68. Theshaft holes 68 have a common center axis 72 that is perpendicular to theprobe center axis 56, but is offset from the probe center axis 56. Theangled orientation of the flanges 66 positions the flange hole axis 72forwardly of the probe center axis 56, as best seen in FIG. 6.

The probe connector assembly 64 also includes a cross shaft assemblyhaving a first shaft 74 that intersects a second shaft 76. The firstshaft 74 has opposite ends that are mounted by bearing assemblies in theprobe flange holes 68. This enables the landing probe 16 to pivot in aradial plane about the flange hole axis 72. As best seen in FIG. 6, aforward shaft end 78 of the cross shaft assembly second shaft 76 has asmaller diameter dimension than a rearward shaft end 82 of the crossshaft assembly second shaft. The second shaft forward end 78 is receivedin the forward bearing assembly 36 of the base, and the second shaftrearward end 82 is received in the rearward bearing assembly 38 of thebase. This enables the probe 16 to pivot in a radial plane about thecenter axis 44 of the bearing assemblies. The connection provided by theconnector assembly 64 between the probe 16 and the base 18 shown inFIGS. 2, 3, and 4 enables the probe 16 to pivot through two mutuallyperpendicular radial planes about the bearing assemblies center axis 44and the probe flange holes center axis 72 relative to the apparatus base18.

The smaller diameter of the cross shaft assembly second shaft forwardend 78 allows this end of the shaft to fail first when an excessiveforce is exerted on the probe 16 due to a rough landing of the aircraft.The collapse of the cross shaft assembly second shaft forward end 78causes a controlled collapse of the probe 16 beneath the aircraft, withthe probe moving forwardly relative to the aircraft, which prevents theprobe proximal end 52 from being pushed upwardly through the center ofthe aircraft fuselage on an excessively hard landing of the aircraft.

Apparatus Struts

Each of the struts 22 shown in FIGS. 2, 3, 4, and 6 has a length withopposite proximal 84 and distal 86 ends. Each of the struts 22 iscomprised of a plurality of elongate links 88 that are substantiallysimilar in construction. Each of the links 88 is connected, end to endby a pivot pin connection 92. The pivot pin connection 92 is provided bya nut and bolt and bushing assembly that connects adjacent links. Theproximal ends 84 of the two forward struts 22 are connected to thedistal ends 28 of the base forward arms 26 by pivot connections 92. Theproximal ends 84 of the rearward pair of struts 22 are connected to thedistal ends 34 of the base rearward arms 32 by pivot connections 92.With the base 18 connected to an aircraft, this provides an operativeconnection of each of the strut proximal ends 84 to the aircraft.

Each of the strut distal ends 86 is connected to the probe 16 by a pivotconnection 19 between the strut distal end and a slip ring 98. The slipring 98 is mounted to the probe 16 for sliding movement of the slip ringalong the probe length. As best seen in FIG. 2, the slip ring 98 ismounted to the probe proximal end portion 62.

As best seen in FIGS. 2 and 3, each of the forward struts 22 has a linkwith an enlarged pivot end 102. The enlarged pivot end 102 of the linkprovides the link with sufficient structural strength to mount aneccentric bushing assembly shown in FIGS. 7 and 8.

Apparatus Eccentric Bushing

The eccentric bushing assembly includes a cylindrical bushing 102 havinga circular center hole 106 that receives the pivot connection 92 betweenadjacent links of the struts. The bushing center hole 106 has a centeraxis 108. The bushing has an cylindrical exterior surface 112 that iseccentric to the cylindrical interior surface of the center hole 106. Acenter axis 114 of the bushing exterior surface 112 is parallel to, butoffset from the center axis 108 of the bushing center hole 106. Acircular flange 115 projects outwardly from the bushing exterior surface112. A plurality of semicylindric notches 116 are provided in thebushing flange 115 and are spatially arranged around the bushing.

The link enlarged pivot end 102 is provided with a cylindrical throughhole 118 that receives the eccentric bushing 104. The bushing 104 isreceived in a snug fit in the hole 18, but is permitted to rotate aboutthe bushing exterior surface axis 114 relative to the link. Asemicylindric notch 122 is provided in the interior surface of the linkhole 118. The link notch 122 has substantially the same dimensions asthe bushing notches 116.

A lock pin 124 is provided for insertion in the link notch 122 and analigned one of the bushing notches 116. By inserting the pin 124 in thealigned link notch 122 and bushing notch 116, the eccentric bushing 104is locked in a set, stationary position relative to the enlarged linkend 102. By removing the pin 124 and rotating the eccentric bushing 104in the link hole 118, the bushing hole axis 108 can be adjustablypositioned along the length of the link and along the length of thestrut 22. By adjusting the position of the bushing center hole axis 108along the strut 122, the overall length of the strut 22 is adjusted.When the eccentric bushing 104 is rotated to its desired positionrelative to the link hole 118 for the desired length of the strut 22,the pin 124 is inserted through the aligned link notch 122 and bushingnotch 116 to lock the bushing 104 in its adjusted position relative tothe strut 22.

Apparatus Strut Variant

FIGS. 9-12 show a variant embodiment of the struts 132 of the aircraftlanding assist apparatus 12. The remaining component parts of theapparatus 12 shown in FIG. 9 are the same, only the struts 132 aredifferent in construction from the earlier described struts 22.

Each of the struts 132 has a length with a proximal end connector 134 atone end and a distal end connector 136 at an opposite end of the strut.The strut 132 includes a flexible band that extends between the proximalend connector 134 and the distal end connector 136. In this embodimentof the struts 132, the band 138 is formed by one or more loops of acomposite material, for example, graphite and epoxy. An elongategraphite strand is looped around the proximal end connector 134 at oneend of the strut, and around the distal end connector 136 at theopposite end of the strut. The epoxy is applied to the looped graphiteand cured to form the final configuration of the flexible strut.

As shown in FIGS. 10-12, both the proximal end connector 134 and thedistal end connector 136 have pivot holes 142, 144. The pivot holes 142,144 are adapted for a pivot connection to an arm of the base 18 and theprobe slip ring 98, respectively.

FIGS. 11 and 12 show the details of the construction of one of the endconnectors 134. Each connector is provided with a pivot bushing 148inserted into the connector pivot hole 144. The connector has a generalU-shaped exterior surface 152 that extends around the connector. A slot154 is recessed into the U-shaped surface 152 of the connector. A loopformed in the band 138 is received in the slot 154. Mutually opposedsurfaces 156 of the slot 154 resist the removal of the looped portion ofthe band 138 from the slot. The engagement of the opposed surfaces 156with the looped portion of the band 138 resists this portion of the bandexiting the slot 154 when the strut 132 is compressed due to movement ofthe probe 16. A projection 158 is formed in one of the slot surfaces 156and a recess 162 is formed in the opposite slot surface 156. Theprojection 158 presses a portion of the looped band 138 into the recess162 and further resists removal of the portion of the band 138 from theslot 154 when the strut 132 is compressed.

On minor compression loads on the strut 132, the bands 138 will bend,but will not pop off the connectors 134, 136. On larger compressiveloads on the strut 132, the looped ends of the bands will squeeze pastthe projections 158. This operation further controls the rate at whichthe strut collapses.

Apparatus Slip Ring Lock Mechanism

FIG. 13 shows a lock mechanism that secures the slip ring 98 in positionon the landing assist probe 16. The slip ring 98 is shown mounted on alower end of the probe proximal end portion 62. The upper end of theprobe distal end portion 58 is shown telescopically received in aninterior bore of the probe proximal end portion 62. As explainedearlier, the conventional construction of a landing assist probeincludes a spring mechanism or shock absorber in the interior of theprobe that biases the probe distal end portion 58 downwardly relative tothe probe proximal end portion 62. The spring mechanism or shockabsorber are not shown in FIG. 14.

The lock mechanism of the slip ring 98 includes a plurality ofsemispherical recesses 164 that are formed into the interior surface ofthe slip ring 98. The semispherical recesses 164 are spatially arrangedaround the interior surface of the slip ring 98. An equal number andsize of circular holes 166 is provided through the proximal end portion62 of the probe. The holes 166 are equal in number to the recesses 164and are positioned opposite the recesses as shown in FIG. 14. Aplurality of balls 168, for example ball bearings, are received in theprobe holes 166. The balls 168 engage against the exterior surface 172of the probe distal end portion 158 and extend through the probeproximal end holes 166 and into the slip ring recesses 164. Thus, in thepositions of the balls 168 shown in FIG. 14, the balls prevent the slipring 98 from moving relative to the probe proximal end portion 62. Justbelow the proximal end portion holes 166, a plurality of elongategrooves 174 are formed in the exterior surface 172 of the probe distalend portion. The grooves 174 are equal in number to the proximal endportion holes 166 and are dimensioned to receive the balls 168 in thegrooves.

As stated earlier, with the balls 168 positioned in the probe proximalend holes 166 and in the slip ring recesses 164 as shown in FIG. 14, theballs 168 hold the slip ring 98 stationary on the probe 16. When acompressive force is exerted on the probe distal end due to contact ofthe probe with a deck of a ship, the probe distal end portion 58 beginsto move upwardly relative to the probe proximal end portion 62. When theprobe distal end portion 58 moves to the extent that the grooves 174align with the probe proximal end portion holes 166, the lock mechanismballs 168 can move into the grooves 174 and out of the slip ringrecesses 164. This frees the slip ring 98 for movement over the exteriorsurface of the probe 16. Thus, on excessive impact of the probe 16 withthe deck of a ship causing significant movement between the probe distalend portion 58 and the probe proximal end portion 62, the lock mechanismof the probe is released and the slip ring 98 is free to move over theexterior surface of the probe 16 controlling the collapse of the probeunder the aircraft.

Apparatus Assembly

FIGS. 14-22 illustrate the steps involved in assembling the aircraftlanding assist apparatus 12 to an aircraft. In the illustrativeenvironment of FIGS. 14-22, the apparatus 12 is retrofit to an AH64Apache helicopter. Again, it should be understood that this is only oneexample of an aircraft with which the apparatus may be employed.However, the steps involved in retrofitting the apparatus 12 to theaircraft are contemplated as being basically the same for other types ofaircraft employing the apparatus.

In retrofitting the apparatus 12 to an aircraft such as a helicopter, itis first necessary to modify the helicopter internal construction toaccommodate the apparatus and the forces involved in using theapparatus. FIG. 14 shows the removal of a bottom fuselage panel 182 fromthe aircraft 14, exposing an interior bay 184 of the aircraft. In theillustrative environment shown, exposing the aircraft interior bay 184also exposes an ammunition container 186 contained in the bay.

FIG. 15 shows the next step in the retrofitting of the apparatus to theaircraft 14. In FIG. 15 the ammunition container 186 is removed from theaircraft interior bay 184, exposing a forward bulkhead wall 188 and arearward bulkhead wall 192 in the aircraft.

The existing forward bulkhead wall 188 and rearward bulkhead wall 192were designed to provide structural strength to the aircraft to supportthe aircraft from its main rotor blades when the aircraft is beingoperated. The bulkhead walls were not designed to receive the impactforces involved with the use of the landing assist apparatus 12 attachedto the underside of the aircraft 14. Therefore, the interiorconstruction of the aircraft requires modification. FIG. 16 shows thenext step involved in modifying the aircraft interior construction wherethe existing forward bulkhead wall 188 is removed from the aircraftinterior bay 184. FIG. 17 shows a replacement, reinforced forwardbulkhead wall 194 being installed in the aircraft interior bay 184 inplace of the removed forward bulkhead wall 188. The reinforced forwardbulkhead wall 194 is provided with reinforced mounting areas 196 thatare designed to receive the impact forces transmitted to the undersideof the aircraft from the apparatus 12 contacting with a ship deck. FIG.18 shows the reinforced forward bulkhead wall 194 completely installedin the aircraft interior bay 184 in place of the removed forwardbulkhead wall 188.

FIG. 19 shows the existing rearward bulkhead wall 192 at the rearwardend of the aircraft interior bay 184. The rearward bulkhead wall 192 isnot removed from the aircraft interior structure in preparing theaircraft for the apparatus 12. Instead, a reinforced rearward bulkhead198 shown in FIG. 20 is inserted into the aircraft interior bay 184 andis secured to the rearward bulkhead wall 192. FIG. 21 shows thereinforced rearward bulkhead wall 198 in the interior construction ofthe aircraft secured to the rearward bulkhead wall 192. The reinforcedrearward bulkhead wall 198 is designed to receive the impact forcestransmitted to the underside of the aircraft by the apparatus 12impacting with a ship deck.

With the reinforced forward bulkhead 194 and reinforced rearwardbulkhead 198 installed in the aircraft interior construction at theopposite ends of the interior bay 184, the previously removed ammunitioncontainer 186 is reinstalled in the aircraft and the bottom fuselagepanel 182 is replaced on the aircraft. The apparatus 12 of the inventionis then installed on an underside of the aircraft with the apparatusbase forward arms 26 transmitting impact forces to the reinforcedforward bulkhead wall 194 and the apparatus base rearward arms 32transmitting impact forces to the reinforced rearward bulkhead wall 198.FIG. 22 shows the apparatus 12 in its retrofit position on the undersideof the aircraft 14.

Apparatus Operation

FIGS. 23-27 show the sequence of operation of the aircraft landingassist apparatus 12 of the present invention. In FIG. 23 the probedistal end 54 just comes into contact with the surface of a ship deck202 during the landing operation of an aircraft to which the apparatus12 is attached. FIG. 24 shows the distal end portion 58 of the probe 16being pushed into the proximal end portion 62 of the probe due to theforce of impact of the apparatus 12 with the ship deck 202 during thelanding operation. FIG. 25 shows the probe distal end portion 58 pushedto its maximum retracted position relative to the probe proximal endportion 62. In this position of the probe distal end portion 58 relativeto the probe proximal end portion 62, the lock mechanism of the probe isdisengaged and the slip ring 98 is free to move along the length of theprobe 16. FIG. 26 shows the slip ring 98 moved upwardly over the probeproximal end portion 62 with one of the struts 204 being pulled intension due to the impact on the probe 16, and the remaining struts 206collapsing under compression forces. The one strut 204 pulled in tensionalso causes the slip ring 98 to move upwardly across the exteriorsurface of the probe proximal end portion 62. In FIG. 27 the probeconnector assembly 64 has pivoted relative to the base 18 to the extentthat the first shaft 74 of the cross shaft assembly has collapsed,controlling the collapse of the probe 16 relative to the base 18 wherethe probe proximal end 52 is prevented from piercing through the bottomfuselage panel 182 of the aircraft.

FIG. 28 shows a view similar to that of FIG. 27, but showing the linkstruts 204, 206 of FIG. 27 replaced with the flexible band struts 208described earlier as the alternative embodiment struts.

The aircraft landing assist apparatus of the invention described aboveis specifically designed to be retrofit to existing aircraft that havenot previously been designed for shipboard landings. On rough landingsof the aircraft using the apparatus, the apparatus is designed tocollapse in a predetermined manner, thereby avoiding any damage toammunition and/or fuel storage areas of the aircraft.

Although the apparatus of the invention has been described above byreference to specific embodiments, it should be understood thatmodifications and variations may be made to the apparatus withoutdeparting from the intended scope of protection provided by thefollowing claims:

1) An aircraft landing assist apparatus comprising: a landing probehaving a length with opposite proximal and distal ends, the probeproximal end being adapted for connection to an aircraft for movement ofthe probe relative to the aircraft with the probe length projecting fromthe aircraft to the probe distal end; a plurality of stabilizing struts,each strut having a length with opposite proximal and distal ends, eachstrut proximal end being adapted for connection to the aircraft and eachstrut distal end being operatively connected to the probe; and, aneccentric bushing mounted on at least one of the struts for rotationalmovement of the bushing relative to the strut, the bushing having a holethough the bushing, the hole having a center axis that is adjustablypositional along the length of the one strut in response to therotational movement of the bushing relative to the strut. 2) Theapparatus of claim 1, further comprising: the bushing having a lockmechanism that selectively locks the bushing to the one strut andprevents rotation of the bushing relative to the one strut. 3) Theapparatus of claim 2, further comprising: the lock mechanism comprisinga pin that is positioned between the bushing and the one strut to lockthe bushing to the one strut. 4) The apparatus of claim 2, furthercomprising: the bushing having a cylindrical configuration with anexterior surface; the one strut having a bushing hole with an interiorsurface, and the bushing being mounted on the one strut in the struthole; and, the lock mechanism comprising a pin that is positionedbetween the bushing exterior surface and the strut hole interiorsurface. 5) The apparatus of claim 4, further comprising: the bushinghaving a plurality of notches in the bushing exterior surface; and, thepin being inserted into one notch of the plurality of notches. 6) Theapparatus of claim 1, further comprising: the eccentric bushing beingone of a plurality of eccentric bushings mounted on the plurality ofstruts for rotational movement of the plurality of bushings relative tothe struts, each bushing having a hole through the bushing and eachbushing hole having a center axis that is moved and adjustablypositioned along the length of one of the struts in response to therotational movement of the bushing relative to the strut. 7) Theapparatus of claim 6, further comprising: each bushing of the pluralityof bushings having a lock mechanism that selectively locks the bushingrelative to the one strut and prevents rotation of the bushing relativeto the one strut. 8) The apparatus of claim 7, further comprising: eachbushing of the plurality of bushings having a cylindrical configurationwith an exterior surface; each strut of the plurality of struts having ahole with an interior surface, one bushing of the plurality of bushingsbeing mounted in each strut hole; and, the lock mechanism of eachbushing of the plurality of bushings comprising a pin that is positionedbetween the bushing exterior surface and the strut hole interiorsurface. 9) The apparatus of claim 8, further comprising: each bushingof the plurality of bushings having a plurality of notches in thebushing exterior surface; and, the pin of each bushing lock mechanismbeing inserted into a bushing notch. 10) The apparatus of claim 1,further comprising: the busing having a cylindrical exterior surfacewith a center axis that is offset from the bushing hole center axis. 11)The apparatus of claim 1, further comprising: the one strut having abushing hole with the busing being received in the bushing hole; a notchin the one strut adjacent the bushing hole; a notch in the bushingaligned with the strut notch; and, a pin positioned in the strut notchand in the bushing notch and securing the bushing against rotationrelative to the one strut. 12) The apparatus of claim 11, furthercomprising: the notch in the bushing being one of a plurality of notchesin the bushing that are selectively aligned with the strut notch inresponse to rotation of the bushing relative to the strut. 13) Theapparatus of claim 12, further comprising: the bushing having acylindrical portion that is received in the bushing hole for rotation ofthe bushing relative to the strut; the bushing having a circular flangethat projects outwardly from the bushing cylindrical portion; and theplurality of notches being in the bushing flange. 14) An aircraftlanding assist apparatus comprising: a landing probe having a lengthwith opposite proximal and distal ends, the probe proximal end beingadapted for connection to an aircraft for movement of the probe relativeto the aircraft with the probe length projecting from the aircraft tothe probe distal end; a plurality of stabilizing struts, each struthaving a length with opposite proximal and distal ends, each strutproximal end being adapted for connection to the aircraft and each strutdistal end being operatively connected to the probe; a bushing mountedon at least one strut for movement of the bushing relative to the onestrut, the bushing having a hole with a center axis that is adjustablypositioned along the length of the one strut in response to movement ofthe bushing relative to the one strut; and, a pin that is engagable withthe one strut and the bushing to lock the bushing in an adjustedposition relative to the one strut. 15) The apparatus of claim 14,further comprising: the bushing having a notch formed in the bushing andthe one strut having a notch formed in the one strut; and, the pin beingremovably inserted in the bushing notch and the strut notch. 16) Theapparatus of claim 14, further comprising: the bushing having anexterior surface with a notch formed in the bushing exterior surface;the one strut having a hole that receives the bushing and a notch in theone strut adjacent the one strut hole; and, the pin being removablyinserted in the bushing notch and the one strut notch. 17) The apparatusof claim 14, further comprising: one of the bushing and the one struthaving a plurality of notches and the other of the bushing and the onestrut having a single notch, the plurality of notches being selectivelyand individually alignable with the single notch in response to movementof the bushing relative to the one strut; and, the pin being in thesingle notch and the aligned notch of the plurality of notches. 18) Theapparatus of claim 14, further comprising: the one strut having a holethat receives the bushing for movement of the bushing in the one struthole relative to the one strut, the bushing hole center axis beingadjustably positioned along the length of the one strut in response tomovement of the bushing in the one strut hole. 19) The apparatus ofclaim 18, further comprising: the bushing having a flange that projectsoutwardly from the bushing over the one strut hole; and, the pin beingengagable with the one strut and the bushing flange to lock the bushingrelative to the one strut. 20) The apparatus of claim 18, furthercomprising: one of the bushing and the one strut having a plurality ofnotches and the other of the bushing and the one strut having a singlenotch, the plurality of notches being selectively and individuallyalignable with the single notch in response to movement of the bushingrelative to the one strut; and, the pin being in the single notch andthe aligned notch of the plurality of notches.